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公开(公告)号：US12091984B2
公开(公告)日：2024-09-17
申请号：US18081844
申请日：2022-12-15
Inventor： Michal Tomasz Kuropatwa , Adam Wojciech Deskiewicz , Robert Kaminski , Adam Kunicki , Nicholas Joseph Kray
CPC classification number: F01D5/027 , F01D5/30 , F05D2220/32 , F05D2240/24 , F05D2260/96
Abstract: A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
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公开(公告)号：US20240117741A1
公开(公告)日：2024-04-11
申请号：US18081844
申请日：2022-12-15
Inventor： Michal Tomasz Kuropatwa , Adam Wojciech Deskiewicz , Robert Kaminski , Adam Kunicki , Nicholas Joseph Kray
CPC classification number: F01D5/027 , F01D5/30 , F05D2220/32 , F05D2240/24 , F05D2260/96
Abstract: A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
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公开(公告)号：US20240344460A1
公开(公告)日：2024-10-17
申请号：US18644422
申请日：2024-04-24
Inventor： Michal Tomasz Kuropatwa , Adam Wojciech Deskiewicz , Robert Kaminski , Adam Kunicki , Nicholas Joseph Kray
CPC classification number: F01D5/027 , F01D5/30 , F05D2220/32 , F05D2240/24 , F05D2260/96
Abstract: A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
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公开(公告)号：US20250163853A1
公开(公告)日：2025-05-22
申请号：US19032996
申请日：2025-01-21
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Jeffrey Donald Clements , Jeffrey S. Spruill , Erich Alois Krammer , Matthew Kenneth MacDonald , Scott Alan Schimmels , Nicholas Joseph Kray , Arthur William Sibbach
IPC: F02K3/06
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000).
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公开(公告)号：US12297751B2
公开(公告)日：2025-05-13
申请号：US18441039
申请日：2024-02-14
Applicant: General Electric Company
Inventor： Anthony Michael Gunasekera , Nicholas Joseph Kray , Leslie Louis Langenbrunner , Simeon Paul Copple
Abstract: A composite airfoil having a non-metallic leading edge protective wrap is provided. In one aspect, the airfoil has a composite core having a pressure sidewall and a suction sidewall each extending between a core leading edge and a core trailing edge. A leading edge protective wrap protects the core leading edge and includes a trailing wrap and a leading wrap. The trailing wrap wraps around the core leading edge and is connected to the composite core. The leading wrap wraps around the core leading edge and is connected to the trailing wrap. The trailing and leading wraps both have leading edges that are spaced from one another. A filler is positioned between the leading edges of the trailing and leading wraps. A protective nose is connected to the leading edge of the leading wrap. The components of the leading edge protective wrap are formed of non-metallic materials.
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Patent Agency Ranking
公开(公告)号：US20250137378A1
公开(公告)日：2025-05-01
申请号：US18496060
申请日：2023-10-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nitesh Jain , Nicholas Joseph Kray , Abhijeet Jayshingrao Yadav
Abstract: A composite airfoil assembly for a turbine engine. The composite airfoil assembly includes a woven core having a core exterior. The woven core includes a first region, a second region, and a transition region. A skin is applied to at least a portion of the woven core at the core exterior.
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公开(公告)号：US12286903B2
公开(公告)日：2025-04-29
申请号：US18173989
申请日：2023-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Thomas Van Oflen , Gary Willard Bryant, Jr. , Michael John Franks , Elzbieta Kryj-Kos , Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A turbine engine having a disk and a composite airfoil assembly. The disk having a slot. The composite airfoil assembly having an airfoil portion, a dovetail portion, and a roll snubber. The dovetail portion having a radially inner surface. The roll snubber being provided on the radially inner surface. The radially inner surface spaced from the slot to define a gap therebetween.
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公开(公告)号：US12280555B1
公开(公告)日：2025-04-22
申请号：US18484510
申请日：2023-10-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arthur William Sibbach , Nicholas Joseph Kray
Abstract: An automated fiber placement assembly forms a component by the placement of separate or multiple layers of fiber tows. The automated fiber placement assembly comprises a cutter assembly defining a cut shape. A backplate is spaced from the first cutter assembly against which cutter assembly can cut the fiber tows. The fiber tows define a longitudinal axis and are fed between the first cutter assembly and the backplate in a feed direction. The cutter head assembly is rotatable and movable to vary the orientation of the cutter assembly in order to define different cut shapes non-orthogonal to the longitudinal axis.
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公开(公告)号：US12241383B2
公开(公告)日：2025-03-04
申请号：US18173952
申请日：2023-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Thomas Van Oflen , Gary Willard Bryant, Jr. , Nicholas Joseph Kray , Arthur William Sibbach , Michael John Franks , Elzbieta Kryj-Kos
Abstract: A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.
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公开(公告)号：US20250052166A1
公开(公告)日：2025-02-13
申请号：US18806969
申请日：2024-08-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
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